Bi-propellant micro-rocket engine
No Thumbnail Available
Identifiers
Publication date
2004
Advisors
Journal Title
Journal ISSN
Volume Title
Publisher
Citations
Export
Abstract
Micro-satellites (from 10 kg up to 100 kg) have mass, volume, and electrical power constraints due to their low dimensions. These limitations lead to the lack in currently available active orbit control systems in micro-satellites. Therefore, a micro-propulsion system with a high thrust to mass ratio is required to increase the potential functionality of small satellites. Mechatronic is presently working on a liquid bipropellant micro-rocket engine under contract with ESA (Contract No.l6914/NL/Sfe - Microturbomachinery Based Bipropellant System Using MNT). The advances in Mechatronic's project are to realise a micro-rocket engine with propellants pressurised by micro-pumps. The energy for driving the pumps would be extracted from a micro-turbine. Cooling channels around the nozzle would be also used in order to maintain the wall material below its maximum operating temperature. A mass budget comparison with more traditional pressure-fed micro-rockets shows a real benefit from this system in terms of mass reduction. In the paper, an overview of the project status in Mechatronic is presented.
Description
Keywords
Type
Citation
Miotti , P , Tajmar , M , Guraya , C , Perennes , F , Marmiroli , B , Soldati , A , Campolo , M , Kappenstein , C , Brahmi , R & Lang , M 2004 , Bi-propellant micro-rocket engine . in Collection of Technical Papers - CANEUS 2004 - Conference on Micro-Nano-Technologies for Aerospace Applications . Collection of Technical Papers - CANEUS 2004 - Conference on Micro-Nano-Technologies for Aerospace Applications , pp. 46-57 , Collection of Technical Papers - CANEUS 2004 - Conference on Micro-Nano-Technologies for Aerospace Applications , Monterey, CA , United States , 1/11/04 .
conference
conference